Sensor for heat or temperature detection and fire detection



June 25, 1968 J. E. LINDBERG. JR 3,

SENSOR FOR HEAT 0R TEMPERATURE DETECTION AND FIRE DETECTION Original Filed April 1, 1963 6 Sheets-Sheet 1 FIRE LEFT ENGINE 3 mvuvron.

MN 5 Lnvpasnc, J4.

FIRE RIGHT ENGINE Q June 25, 1968 J. E. LlND BERG, JR 3,390,

SENSOR FOR HEAT OR TEMPERATURE DETECTION AND FIRE DETECTION Original Filed April l, 1965 e Sheets-Sheet 2 FIG. 5 m m r E T FIG.6 D

as 7: M i' 75/8 IHIDIIIIIIIIIIIIIII INVENTOR.

JOHN E. L/IVDB R6, JR. BY A A a 47' TORNE Y June 1968 J. E. LINDBERG, JR 3,390,365

SENSOR FOR HEAT OR TEMPERATURE DETECTION AND FIRE DETECTION Original Filed April 1, 1963 6 heets-Shee 3 37 FIG 9 37 p43 76 p 77 .94 I 2 x CURVE F THRESHOLD POINT 6 FIG. I3

VOLUM 0;- VOLUME JO! SENSOR SENSOR CHAMBER r IN RESPONDER I l I 1 PASSAGE vow: PROPORTION FILLED .IWTI'I FILAMENT E INVENTOR.

JOHN E. Ll/VDBERG, JR.

A TTORNE Y June 25, 1968 J. E. LINDBERG, JR 3,390,365

SENSOR FOR HEAT OR TEMPERATURE DETECTION AND FIRE DETECTION 6 Sheets-Sheet 4 Original Filed April 1 1963 FIJI FIG. l5

INVENTOR. Jaw E lovoazna. JR.

June 25, 1968 SENSOR FOR HEAT 0R TEMPERATURE DETECTION AND FIRE DETECTION Original Filed April 1, 1963 FIG. l8

J. E. LINDBERG, JR

6 Sheets-Sheet 5 TEST OVERHEAT' TEST FIRE INVENTOR.

Jaw/v f. l/NOBERG JR.

ATTORNEY June 25, 1968 J. E- LINDBERG, .JR 3,390,365

SENSOR FOR HEAT OR TEMPERATURE DETECTION AND FIRE DETECTION Original Filed April 1, 1963 6 Sheets-Sheet 6 FIG. 20

I ac-rs FIG. 22

IN V EN TOR.

PRESSURE Gauss m HYDROGEN DETECTOR United States Patent 3,390,365 SENSOR FOR HEAT 0R TEMPERATURE DETECTION AND FIRE DETECTION John E. Lindberg, Jr., 1024 Adrienne Drive, Alamo, Calif. 94507 Original application Apr. 1, 1963, Ser. No. 271,043, now Patent No. 3,277,860, dated Oct. 11, 1966. Divided and this application Sept. 9, 1965, Ser. No. 516,800

7 Claims. (Cl. 337-299) ABSTRACT OF THE DISCLOSURE This temperature-detection device disposes in an imperforate enclosure metallic hydride of the type that reversibly releases and takes up hydrogen, releasing it when heated above a threshold temperature. The metal of the hydride has a melting point above the highest temperature to which the sensor is to be subjected, under the pressure conditions obtaining within the enclosure. A continuous passage for gas is provided within the enclosure, and the gas is used to actuate a pressure switch that is connected to the enclosure. The pressure switch preferably is of the diaphragm type, preferably of molybdenum, and the chamber on the opposite side of the diaphragm from the enclosure may be prepressurized, and the pressure therein may be varied.

This application is a division of application Ser. No. 271,043, filed Apr. 1, 1963, which was a continuation-inpart of application Ser. No. 102,622, filed Apr. 10, 1961, now abandoned, which was a continuation-in-part of application Ser. No. 815,406, filed may 25, 1959, now U.S. Patent No. 3,122,728.

This invention relates to improvements in heat or temperature detection and especially fire detection.

The invention is characterized by its provision of a novel nonelectric heat-detecting element or sensor. Only this detecting sensor need be located in a fire zone (or other heat-detection zone), and it is connected, preferably outside the zone, to an electrical warning or corrective system, preferably by a pressure-sensitive instrument that I term a responder. The responder may be located outside the zone in which detection is desired, though usually close to it, or it may be located in that zone. The actual alarm or heat-condition indicator can be connected to the responder by a Wire of practically any desired length. For example, the nonelectric heat-detecting sensor may be inside a house, the responder just outside the house, and the indicator at the fire station. Or the nonelectric heatdetecting sensor may be in zone 1 of an aircraft engine, ahead of a fire wall; then the responder may be on either side of the fire wall and the indicator on the aircraft in- 1 strument panel.

Furthermore, the novel heat-detecting sensor may be filamentarya long, very-narrow-diameter, hollow tube. It may extend along a line, around a circle, or along any desired path and for quite a considerable length.

The advantages of the invention in home fire-detection systems will at once be apparent. Less apparent may be the extremely valuable use of the invention in regions inaccessible to direct observation, such as the interiors of aircraft engine nacelles and other remotely located installations of power-generating equipment. The invention is useful for detecting fire or overheat conditions at any point in any vehicle or building, and has numerous commercial and industrial applications.

An important object of the invention is to provide an 3,390,365 Patented June 25, 1968 ice improved fire-detection system for use in aircraft in zone 1, ahead of the fire wall of the power plant, such as the region in an engine nacelle ahead of the fire wall. A corollary object is to provide a system that will meet the requirements of the pertinent government regulations.

Conventional fire detectors that have been employed in aircraft for zone-l fire detection,'whether of the continuous type or of the single-point type, have relied upon electrical circuits that extend into the fire zone. For example, a prevailing type of continuous fire detector is actuated by the change in electrical resistance of semiconducting materials caused by a change of environmental temperature. The trouble has been that false alarms have plagued all heat and fire-detecting systems relying on electrical detecting circuits extending into the fire zone. For example, the moisture conditions in the engine chambers, where Zone-l detectors are located, very considerably, because changes in altitude radically affect the temperature and pressure conditions there. As a consequence, moisture condensation occurs frequently and has often caused electrical fire-detectors to develop low-resistance shorts that resulted in false alarms.

False alarms are serious enough on the ground, as everyone knows, but in aircraft they are unforgivable, because the crew must immediately take hazardous and expensive emergency action. Recent statistics indicate, for example, that one the commercial airlines in the United States alone there are, on the average, two false fire warnings every day. Each false warning is liable to cause a fatal crash, and several of these have occurred each year in recent years. Even when the plane and passengers are saved, each false fire warning requires immediate remedial action, such as dumping excess fuel down to the allowable landing weight and landing as soon as possible, and the resultant disruption of the schedule, the cost of landing, taking off, and obtaining clearances, and other expenses resulting from this false warning have been estimated to average more than $20,000 additional expenditure per false fire warning requiring landing.

Current statistics show that there are more than false fire alarms on jet-engine aircraft for every true alarm thereon.

The present invention solves the problem of preventing moisture and other atmospheric conditions from causing false alarms, and it does this by using a sensor that is never actuated by moisture or by atmospheric conditions.

This invention also eliminates other factors that led to false alarms or failures in prior-art devices. Such problems as moisture condensation in voids at the joints between successive elements of continuous-type detectors and the accumulation of foreign material in the connections, both leading to low-resistance shunt paths between the inner conductor and the outer shell and hence to false warning, cannot occur in this invention.

Some prior-art types of fire detectors have given false alarms because they responded to the rate of change of temperature rather than, or in addition to, a predetermined high temperature level. Consequently, during airplane takeoff, when the temperature in the power-plant area increases 'very rapidly, these detectors tend to give false alarms when everything is normal. The same thing happens during rapid climbing and some other operating conditions. The device of this invention can be made independent of the rate of change of temperature; so another source of false alarms is obviated.

Prior-art continuous-type fire detectors also gave false alarms whenever the detector element was seriously dam aged, because short circuits were then caused within the o,o 3 element. The sensor of the present invention can be completely severed, cut open, dented, or bent in any fashion without causing a false alarm.

Another object of the invention is to provide a fire detector substantially lighter in weight-per-length then previous fire detectors, an important feature because every pound saved in equipment means that additional payload is available. In modern transport aircraft, each pound saved in manufacture is considered to be worth about $50 to $350, depending on the type of aircraft. The fire detector of the present invention weighs only about oneseventh as much as typical comparable prior-art detectors.

A further object is to provide a fire detector capable of indefinitely recycling, giving warning each time a critical elevated temperature is reached and withdrawing the warning each time the temperature drops.

Another object is to provide a fire-detection system which avoids the complexities characteristic of the circuits and mechanical elements of other fire detectors. For example, no amplifiers or relays need be used in this system.

Another object is to provide a completely hermetically sealed heat-detection transducer, entirely free from environmental errors caused by such things as pressure and altitude changes, moisture condensation, and so on.

Another object of this invention is to provide a system which will both: (1) detect and warn when the arithmetically average temperature of a long (e.g., 20-foot) continuous detecting element or sensor exceeds a preset warning level (e.g., 350 F.), and (2) give a fire warning when any small section of the sensor-cg, about A1" longexceeds the fire temperature, e.g., 1500 F. or above. In a particular embodiment, the system will also give addi tional overheat warning at both a different average temperature and when the small section, e.g., about A" long, exceeds a chosen temperature in between the set average and the fire temperatures.

An additional object is to provide a device capable of indicating average temperatures in two well-defined temperature ranges. Further, sharp changes in the pressuretemperature response characteristics, which occur at the transition point between these two ranges, may be utilized to indicate certain temperature conditions.

A further object is to provide apparatus for detecting two difierent average temperatures with a single instrument.

Another object of the invention is to enable the use of several nonelectric heat-detecting transducers in combination with a single electrical circuit, to achieve simplicity while still pin-pointing which transducer has been actuated and to what extent it has been actuated.

Other objects and advantages of the invention will appear from the following description of several preferred embodiments thereof.

In the drawings:

FIG. 1 is a diagrammatic view in elevation of a firedetection system embodying the principles of this invention, so installed as to detect fire in a house and give an alarm in a fire station, when and if fire does occur in the house. The broken line in the conductor indicates that the distance between the house and the fire station is not shown and can be any such distance as is commonly encountered.

FIG. 2 is a diagrammatic fragmentary view in perspective of a portion of an aircraft containing a fire-detection and warning system embodying the principles of this invention.

FIG. 3 is a fragmentary view in elevation of a portion of the instrument panel of the aircraft of FIG. 2, showing the warning lights of that fire-detection system.

FIG. 4 is an enlarged view in elevation and in section of a simplified form of fire-detection system, as may be used in FIGS. 1 and 2. It shows the responder and a heatdetection sensor that is broken in the middle to conserve space. The electrical circuit is shown diagrammatically.

FIG. 5 is a greatly enlarged view in elevation and in ection of a portion of one preferred form of a heat-detec- FIG. 7 is a view similar to FIG. 5, of a modified form of sensor, also embodying the principles of the invention.

FIG. 8 is a view similar to FIG. 5, of another modified form of sensor.

FIG. 9 is a view generally similar to FIG. 5, of still another modified form of sensor.

FIG. 10 is a view similar to FIG. 5 of a further modified form of sensor.

FIG. 11 is a graph plotting internal sensor pressure as a function of its average temperature in a particular application of the invention.

FIG. 12 is a view somewhat like FIG. 4 of a modified form of responder.

FIG. 13 is a bar graph illustrating the relative proportions of the volumes in the sensor tube, both occupied and passage space, and the volume in the sensor chamber of the responder.

FIG. 14 is a view similar to FIG. 4, of another modified form of responder and a modified electrical circuit, in a heat-detection system employing a single sensor (like that of FIG. 8) to indicate both fire conditions and overheat conditions at a level below the fire level. The system also includes a test mechanism.

FIG. 15 is a fragmentary view in elevation and is section, of a fire wall installation of a responder like that of FIG. 14.

FIG. 16 is a fragmentary, somewhat diagrammatic plan view of an aircraft having a system like that of FIG. 14, installed along with a fire extinguisher system.

FIG. 17 is a fragmentary view in elevation of a portion of the instrument panel of the aircraft of FIG. 16, showing two warning lights, a bell, and two test-switch buttons.

FIG. 18 is a simplified diagrammatic view, partly in elevation and in section, of a system incorporating several fire detector units of the type depicted in FIG. 14 combined with a single electrical circuit.

FIG. 19 is an enlarged view in elevation and in section of a portion of a fire-detector responder of this invention, incorporating a modification also utilizing the principles of the invention.

FIG. 20 is a somewhat diagrammatic enlarged view in section of a modified form of sensor-responder combinatlon.

FIG. 21 is a view similar to FIG. 20 of another modification.

FIG. 22 is a view similar to FIG. 4 of a modified form of system in which a pressure gauge or hydrogen detector is used in the combination.

(A) GENERAL STATEMENT OF THE INVENTION As shown in FIGS. 1 and 2, the fire detection system of this invention comprises 1) a nonelectric detection means, preferably in the form of a generally filamentary sensor A or indeterminate length, (2) a responder B, and (3) and electrical circuit C. The function of the sensor A is to actuate the responder B, and the function of tht responder B is to actuate the electrical circuit C in response to predetermined conditions of temperature obtaining in the environment Within which the sensor A is located. Thus, the sensor A and the responder B, considered together, comprise a transducer.

The sensor A may be further defined in general terms (see FIGS. 4-10) as a generally filamentary enclosure D of extended length connected to the responder B and containing means E responsive to heat in the environment of the sensor A, forraising the pressure in the responder B.

The responder B may he thought of as typicaliy a pressure-actuated electrical switch that opens or closes the electrical circuit C in response to pressure changes induced by the sensor A as a result of the effect of temperature on the sensor A.

The electrical circuit C may be a warning circuit or a remedial circuit. Several responders B may be used in one circuit, if desired, to control it in some manner that depends on the temperature conditions of the environments to which the sensors A are exposed.

(B) GENERAL ILLUSTRATION OF THE INVENTION (1) A home installation (FIG. I)

The fire detector system of this invention may be used to give instant alarm in a fire station when there is a fire in a home. For example, as shown in FIG. 1, the detector element or sensor A may be disposed along critical locations in John Does house 50; such as in an attic 51. immediately beneath and above a ceiling 52, down one or more walls 53, and along one or more floors 54. As will be shown presently, the sensor A may comprise a thin, generally filamentary tube and may be quite inconspicuous when installed.

The responder B may be located just outside the house 50 and is an actuator that closes an electrical circuit C, none of which extends inside the house 50. The circuit C includes a conductor 55, such as copper wire that leads to an alarm panel 56 in a fire station 57. The circuit C may have its power supply 58 located in the fire station 57. The panel 56 may include a bell Or buzzer or other audible warning (not shown) as well as a signal light 59 identifying the house 50 as John Docs house. There may be as many lights 59 on the panel 56 as there are homes having the warning system installed; so each house can be instantly identified.

When a fire occurs in John Does house St), the sensor A is heated. In a manner explained later, the rise in temperature increases the pressure inside the sensor A, and this pressure sets on the responder B almost instantaneously, closing the circuit C (in a manner also explained later). Upon closure of the circuit C, current flows through the conductor 55 and lights the light 59, also giving audible Warning if desired. The men in the fire station can take immediate remedial action to save John Does house.

(2) An aircraft installation (FIGS. 2 and 3) The system of this invention has many features especially suitable to use in aircraft. Just to give a general picture that can be referred to from time to time, FIG. 2 presents an aircraft 60 in which a system of this invention is installed. The nonelectrical sensors A are used, one for each of the two engine nacelle-s 61, 62 of this airplane 60. The sensors A are disposed at critical locations in the nacelles 61, 62, usually around the engines, and the responders B are mounted on the fire walls 63, 64. The circuits C include conductors 65, 66 leading to espective lights 67, 68 on the instrument panel 69 (FICl. 3). Again, there may also be audible warning, but it not illustrated in these general views.

Fire at either engine nacelle 61 or 62 heats the sensor A therein and causes its associated responder B to actuate its associated circuit C, thereby lighting the light 67 or 68. The installation is simple, compact, economical, light in weight, and- -as Will soon be seeneffective.

With these general pictures in mind, we can proceed to a more detailed description.

(C) THE SENSOR A The fire detector of this invention includes a novel detecting means or sensor A. The sensor A has a gastight enclosure D, preferably comprising a narrow-diameter metal tube of constant cross-sectional area and of any desired length. Within this enclosure D is a selected metallic hydride E responsive to the temperature of the enclosure D to releasing hydrogen for varying the pressure inside the enclosure D, acting as a transducing or gas-liberating agent. Preferably, the enclosure D also contains a noble gas such as argon, which acts as a temperature averaging device and also performs several other key functions that will be explained later. The only opening in the enclosure D is connected to and sealed to the responder B, which itself defines a closed chamber connected to the enclosure D. An alteration of the internal pressure within the enclosure D therefore affects the responder B.

(1) Discrete temperature detecti0nindication when even a fraction of an inch of the sensor reaches a critical temperature (a) The metallic hydride E.-The metallic hydrides E used in this invention release large volumes of hydrogen gas when elevated to a temperature sought to be deected and take up this hydrogen when cooled. Although these hydrides and some of their characteristic phenomena have been observed for many years, the main practical applications of them heretofore have been in the vacuum tube industry, where the metals that form these hydrides are used to take up or getter residual gases in the tube after sealing. Therefore, the metals of these hydrides have been known as getters.

With the alkali and alkaline earth metals, i.e., Groups I-A and II-A of the Periodic Table, hydrogen forms stoichiometric ionic compounds, such as sodium hydride and calcium hydride, in a reversible reaction. Specifically, hydrogen reacts with lithium, sodium, potassium, rubidium, cesium, calcium, strontium, and barium, in stoichiometric proportions to form hydrides. However, for airplane fire detection these materials are unsatisfactory, because of the low melting points of the metals, which makes them prone to fiow and plug the tube D. Moreover, these hydrides react rapidly and often violently with water or even air, so that if the encasing tube were broken, a violent reaction would ensue, possibly starting a fire and possibly giving a false alarm.

With the elements of Groups IILB (including the rare earth and actinide elements IVB, and V-B of the Periodic Table, and with palladium, hydrogen forms hydrides of a different type. The amount of hydrogen that combines with or dissolves in these elements varies directly with the square root of the pressure, and it decreases with increase in temperature. They do not r act violently with water and do not melt until very high temperatures. These are the metals whose hydrides are used in the airplane fire detector of the present invention. Broadly, the class consists of scandium, titanium, vanadium, ytterbium, zirconium, niobium, palladium, hafnium, tantalum, the rare earth metals (atomic numbers 57 through 71), and the actinide metal (atomic numbers 89 through 103), and alloys thereof. As a practical matter, however, most of the actinides can be eliminated because of their great cost and radioactivity. So can most of the rare earth metals and some of the others, because of cost or unavailability, the most practical metals being titanium, vanadium, zirconium, palladium, niobium, and tantalum. Hafnium is found in zirconium as a trace impurity and appears to act like zirconium. Alloys such as titanium-zirconium and titanium-vanadium are also useful and practical. Examples of the sorptive capacities as a function of temperature of some of these materials are given in Tables I and II.

TABLE I.SORPTION OF HYDROGEN BY TYPICAL MET- ALS OF GROUP B [In cm. (S.l.P.) per gm., at 1 atm.]

Temperature, C. Titanium Vanadium Zirconium TABLE IL-IIYDROGEN CONTENT OF CERTAIN HY- DRIDES A'l ROOM TEMPERATURE Hydrogen content (S.T.P) in cc.

The amounts of hydrogen contained are thus very large, so that substantial pressure changes result upon its release. This means that a long continuous sensor tube D with about half its cross-section filled with hydride will produce a tremendous pressure increase when even a small portion of its length is heated to a fire temperature; a twenty-five foot tube can have a marked change in pressure when only one-quater of an inch is heated to 1500 F., the rest of the tube remaining at room temperature.

These materials, when located within a closed chamber, thus provide an effective means of altering the internal pressure of the chamber, in accordance with the temperature of all or of only a small portion thereof. This internal pressure is a function of the temperature applied to the material. In general, above a threshold temperature an increase in pressure results from each incremental increase in temperature. Thus, the enclosed material functions as an element which effectively converts temperature variations into pressure variations, and for that reason the hydrides used here may be thought of and referred to as transducing agents.

(b) The problem of reaction between the getter E and the tube D.The sensor tube D is a non-porous tube, preferably of constant cross-sectional area. In all cases there has to be passage means for transmitting the pressure changes along the tube and to the responder B. In applications where the tubes D are to be bent or curved around corners, the tubes D are preferably made from suitable metals such as stainless steel, nickel or molybdenum, for example. In applications where bending is not required and minimum diffusion is desired, the tube D may preferably be made from non-porous quartz or ceramic. A typical sensor tube D is preferably about 0.030 to 0.060" outside diameter with a wall thickness of preferably about 0.005" to 0.015". Such tubes D are preferably about one to forty feet long, although they may be longer or shorter.

The inner surface of the tube D should not react with the materials it contacts, including the getter metal E inside it, over the temperature range in which the sensor is to be used. However, the preferred materials for the tube D may be reactive with a preferred transducing agent E at the temperatures involved, so that a difiicult problem must then be solved. Thus, when such getter metals as titanium and zirconium are used, especially under ultraclean high-vacuum conditions assuring their proper ingassing and outgassing of hydrogen, there is liable to be a reaction between the titanium or ziconium and an encasing metal tubing at the high temperature which the sensor is intended to sense. This phenomenon has been noted with tubings of various metals, including stainless steels such as Nos. 302, 303, 321, and 347, and also with pure iron and pure nickel. The reaction between the tube metal and the getter metal tends to form an alloy which melts at a much lower temperature than either of the two metals involved, thereby weakening various points along the encasing walls; then the high pressure of the outgassed hydrogen, the high temperature, and the flowability of the alloy soon combine ot burst a hole through the wall of the tubing. Often, a hole will open even without high internal pressure. This reaction apparently occurs primarily with the outgassed metal, not with its hydride, the hydride apparently acting as a partial preliminary protector, but at the vital operating temperatures, the outgassing of the hydrogen results in pure metal, which then reacts with the tube metal.

A further problem created by this reaction is the fact that this alloy tends to flow and plug the tube, thus putting a partition across the tube and creating even higher than normal pressures at a given temperature in that portion of the tube and blocking the transmission of the warning pressure to the responder. The only materials which I have found satisfactory for use directly adjacent to zirconium and titanium and others like them (under these conditions) are molybdenum, tungsten, and ceramics such as aluminum oxide and beryllium oxide; also the reaction between the getter metal and quartz occurs rather slowly, and quartz tubes may be used for limited environmental applications. For normal temperature range application, palladium can be used as a getter within most types of encasing tubes without reaction, but a about 2000 F., reaction does occur; so if it is to be used at or even subjected to such high temperatures, the naked palladium metal cannot be used within stainless steel tubes. Below these temperatures, palladium can also be used next to the zirconium and titanium without reaction. For many uses, vanadium and tantalum can be used in stainless steel tubes without reaction.

Some degree of improvement may be obtained by lining the tube with the oxide of the tubing metal; however, in high temperature operation, this, too, breaks down. The reducing atmospheres occasioned by liberation of by drogen from the hydride apparently helps to remove the protective oxide film.

'Metal tubings of molybdenum, tungsten, or platinum, or their alloys can safely come into contact with such getter metals as zirconium and titanium at these high temperatures; however, tungsten tubing is not ordinarily available, due to its serious fabrication problems, and molybdenum tubing, though available, is practical only in quite short lengths, up to about four feet, in the diameter range needed for fire-detector sensors. Also platinum tubing is quite expensive. Fabrication of either molybdenum or tungsten or their alloys into tubing is exceedingly difiicult, due to their inherent brittleness and to the rapid work-hardening resulting from the tubular draw formation. Further, molybdenum and tungsten are unable to stand direct exposure to flame and oxidizing atmospheres, for they have rapid oxidation deterioration at relatively low temperatures, far below the actual flame temperature of 1500 to 2000 F. found in practice. Protective coatings for these materials normally increase their brittleness and, to date, have not been very successful. Also, the cost of such tubing is prohibitive.

For many uses it is essential to use metal tubing of metals which can be flexed and which can stand flame. Stainless steel and nickel are examples of suitable tubing, but then there is the reaction problem.

(c) Solution to the reaction problem; a wrapped getter filament (FIGS. 4-6).-The present invention provides a solution to this diflicult problem, by encasing the hydride in a novel gas-porous protective wrap before putting it into the tubing. FIGS. 4 to 6 show a preferred form of transducing agent E enclosed in the sensor tube D. Here the transducing agent L is a filament 25, such as zirconium wire, and may be about 0.005 to 0.020" in diameter, for example. A ribbon 26 of suitable material, such as molybdenum, tungsten, platinum, and rhenium, preferably about 0.020" wide and 0.002 thick, is wrapped tightly around the filamentary transducing agent 25 and fits within the tube D. The ribbon 26 physically spaces the filament 25 from the walls 27 of the tube D and prevents the transducing agent 25 from fusing or welding to the tube walls 27, even in the event that the sensor A is exposed to extreme heat. The ribbon 26 and wrap 27 fill approximately half of the space inside the tube D, leaving the remainder available for passage of the gas and transmission of the pressure changes along the tube. The spiral space between successive turns of the ribbon 26 may provide the passage means for the gas when the wire 25 is fully ingassed so that the ribbon 26 is forced substantially into contact with the tube walls 27. The strip 26 should be wound to fully cover the wire 25; even overlapping will not stop the passage of hydrogen, and ideally a pitch equal to the axial width of the spirally wound strip is preferred.

Other porous nonreactive barrier wraps may be used around the filament 25, such as plaited or woven wire meshes 28 of molybdenum or platinum (see FIG. 7), resembling the typical shielding sleeving familiar in electronics, except that here the size is smaller.

An important function of the barrier wrap 26 or 28 is to assure passage for gas at all times through the tube D between the core or filament 25 and the walls 27. Even if the tube D is mashed or hammered down or bent double and hammered, the irregularity provided by the wrap provides a passage through which hydrogen can pass freely, hydrogen being the most mobile of gases.

As a simplified example of installation of the sensor A of FIG. to the responder B, one end 30 (FIG. 4) of the tube D may be connected by a gas-tight seal to the responder B, while the other end 31 of the tube D is still open. This free end 31 may be connected to a vacuum pump and the tube D pumped free of gas. Then the tube D is heated, pure hydrogen is forced in through the free end 31, and then the zirconium filament 25 absorbs the hydrogen while it cools. The originally pure metal 25 is converted into an ingassed hydride, expanding about 15% as it does so. The molybdenum wrap 26 moves and expands somewhat to accommodate this. The fully ingassed (expanded) state is shown in FIG. 6, while the fully outgassed (reduced) state is shown in FIG. 5. The free end 31 is then sealed off, and the device is ready for operation. While this fairly crude procedure illustrates the general principle, a refined method giving more consistent and greatly improved results is disclosed in a copending patent application Ser. No. 180,121, filed Mar. 16, 1962.

As stated, it is preferable that the space between successive edges of the ribbon 26 in its spiral wrap be as close together as possible, though the sensor will function satisfactorily with a reasonable gap or with overlap. There is no difficulty in getting the gas to go in and out due to any pressure of one wrap on the other. The desire for the minimum spacing between laps is that if any small particle could get out through the space between laps, it then might react the encasing tube. To picture this, one must understand that in the process of ingassing, the hydride grows approximately 15% (see FIGS. 5 and 6), and on its ingas/outgas cycling, this change in demension often results in fracture of the wire 25, inasmuch as the hydride is highly brittle. Normally, the filament 25 and the ribbon 26 break into segments which have a length of approximately 1 to 10 times the diameter of the filament 25. But, in such fracture, it is always possible that a small granule is separately fractured, and if it could pass through a space between successive laps of the spiral wrap, it would outgas upon being heated during operation and then the getter metal would tend to react with the encasing tube and cause failure of the tube. By properly wrapping the wire 25 with the ribbon 26 with minimum space between laps, such fragments are retained inside the ribbon wrap and cannot gain access to the tube wall 27.

In using the molybdenum wrap, care is preferably taken to shear the end of the ribbon-wrapped core in such a manner that part of the ribbon rolls over the end of the sheared getter wire, providing a retaining protective member to prevent a part of the getter from coming out of the end of this porous molybdenum containing member. Dull shears will do this. Further, to insure protection, it is desirable to add at each end of the wrapped filament 25 a short length 32 of tungsten or molybdenum filament, which may be made from several (e.g., 2 or 3) such wires twisted together. The filament 32 is of large enough diameter so that it cannot axially override the filament 25, and the filament 32 is small enough so that it does not bar the passageway to the gas. The piece 32, ordinarily about one-quarter inch to several inches long, acts as a barrier to assure that no particle of getter metal touches the reactive encasing material. Beyond the piece 32, at the end 30, a small mandrel wire (not shown) is inserted into the tube D and the walls are crimped at 33 to provide a retention means for the piece 32 and filament 25, while leaving a capillary passage 34 after the mandrel wire is withdrawn. Then one or more brazing wires 34 are installed into the end 31, into contact with the wire 32 at that end, and that end is sealed by fusing the brazing wire. Thus the wire 25 can nowhere touch the walls 27.

(d) Another solution to the reaction problem; use of granular materials (FIG. 8.-Another way of preventing reaction between the getter and its encasing tubing employs a mixture of powdered getter metal 35 and aluminum oxide 36 (or silicon dioxide (FIG. 8), with the oxide powder 36 so fine relative to the getter particles 35 that it coats the surfaces of the getter granules 35 and, therefore, acts as a barrier to prevent contact and resultant reaction with the tubing walls 27 It also acts as a barrier between the hydride particles 35 themselves, so that they do not interact and form larger granules which might plug the tube. The particles size of the aluminum oxide 36 is preferably in the order of a few millionths of an inch, and the granule size of the hydride 35 is preferably in the order of 200-500 mesh; however, the particle size of the hydride is less critical. The aluminum oxide or silicon dioxide 36 should be microscopic to coat and adhere properly to the hydride granules 35. Some reaction takes place between the hydride and silicon dioxide, but this causes no damage and in fact often helps by aiding in maintenance of a coated film around each granule. This system can be used in filling stainless steel and similar metal sensors and is successful in preventing reaction with its incasement. Other ceramic-type oxides, including beryllium oxide and alumina in powdered form, are also suitable.

(e) Use of non-reactive ceramic tubes (FIG. 9).--The use of ceramic or quartz tubes 37 in short lengths with connecting couplings of small bore (capillary) ductile tubing 38, such as stainless steel, with the getter 25 confined solely to the ceramic or quartz tubes 37, as by reduced-diameter end portions 39 thereof, is useful in certain applications such as temperature control in jet engines, because the ceramic tubing can stand the very high temperatures there better than can metal. The nonfiexible ceramic members 37 is placed Within successive heat zones, such as behind or in the burners Within a jet engine, and the capillary ductile tubing 38 is placed in areas not requiring sensing, acting as a jumper between the successive ceramic tubes 37 while its capillary lumen 40 holds the unoccupied volume or passage space to a minimum so that effect of the emission of hydrogen on the pressure is maximized. The diffusion rate of gas through the ceramic and quartz is almost nil, being orders of magnitude less than that of the diffusion through any known metal.

The getter within these ceramic tubes 37 may be raw getter wire 25, as shown in FIG. 9, but, preferably, is either the powdered mixture 35, 36 or a contained getter wire, i.e., a filament 25 contained in a wrap 26 or 28. The reason for this is that if no inter-granule protection is provided, as with the powdered material 35, 36, or if no porous, non-reactive enclosing structure is provided, as with the molybdenum or tungsten ribbon wrap 26 or wire wrap 28, the getter tends to coalesce at high temperature into a solid body preventing proper passage of gas. In the case of powdered materials 35, this can result in complete blockage and lamost vacuum tight conditions. This coalescing is apparently partly due to crystallization and growth, and when this granule material 35 takes up hydrogen, it greatly increases its size and therefore tends to put a high-pressure sealed plug within the tube D, preventing gas passage. The same thing is true wherever the hydrides of this invention are concerned, including such metals as tantalum and vanadium that do not readily react with stainless steel and might not otherwise require encasement.

The sensor A of FIG. 9 may also represent a filament 25 of vanadium or tantalum hydride in a stainless steel tube D, for no special protection is required with these materials, but again a protective wrap is preferred, for it will prevent coalescence of the fractured particles and resultant plugging of the tube D. The filament 25, of whatever material, may itself be tubular, if desired.

(f) Other forms of the sensor A (FIG. l).-The transducing agent E may be used in the form of a series of discrete pellets 41 as shown in FIG. 10. The pellets 41 may be formed by molding or pressing a mixture of granular powdered hydride with ceramic powder, for example, possibly using a binder, compressing the mixture into pellet form. Or the pellets 41 may be made from vanadium, tantalum, or palladium hydride. The pellets 41 are made slightly smaller than the inside diameter of the tube wall 27 to allow passage of gas evolved from the pellets 41.

Although only a few specific forms for the agent B have been illustrated or described, others are possible, and it is intended that their omission not be in any sense limiting or restrictive to the possible application and construction of this invention.

(2) Average temperature indication As stated earlier, the hydrogen is, at cool, normal temperatures, completely held in the metal, as a hydride. Its release begins only at a threshold temperature and then takes place extremely rapidly, so that it can be used to indicate the reaching of a critical temperature of a very short length of the sensor, say /4.

However, it is also valuable for the sensor A not only to indicate when /4" thereof reaches a temperature of, say, 1500 F. but also to indicate when an arithmetical average temperature of a zone reaches a much lower temperature, say 350 F. This is done by the same sensor A in the present invention by incorporating therein a noble, nonreactive gas, which fills the passage area between the hydride and the tube walls to some desired pressure, e.g., one atmosphere. For this purpose, the cross-sectional passage area should be uniform, and the volume of the sensor chamber in the responder should be as small as possible.

Furthermore, the noble gas not only enables detection of a critical average temperature but also produces some other very important and quite unexpected and unpredictable results.

Also, the heat-detection apparatus of this invention, by virtue of the unique character of the relation between the temperature of the sensor A and the pressure in the sensor A, is capable of indicating average temperatures in two distinct ranges as well as giving response to relatively strong local heating at any point along the sensor A.

By way of clarification, the term average temperature as used here means the arithmetic average over the whole sensor A of the temperature of each incremental length of sensor. Expressed mathematically, the average temperature is given by:

where L is the total length of the sensor, x is the distance along the sensor, and T(x) is the temperature of the sensor at the point x.

For temperatures above a certain point, known as the threshold point, the relation between the temperature of a hydride, of the type used in a sensor of this invention, and the pressure in the sensor is linear, at least within a wide working range. Below the threshold point the hydride does not liberate gas, and so the pressure in the sensor depends only upon any free gas which may be present in the sensor. As said, preferably there is a noble gas at a normal pressure of one atmosphere. The pressuretemperature relationship for the free gas is also approximately linear as governed by the laws of ideal gases. Thus the pressure-temperature relationship for a sensor of this invention is linear in the range lying wholly below the threshold point and in the range lying wholly above the threshold point, but the constant of proportionality is different in the two ranges.

The pressure-temperature curve for a typical sensor of this invention is shown somewhat schematically in FIG. 11. It will be seen that the curve consists of two straight lines, curve F representing the free noble gas and curve H representing what happens when the outgassed hydrogen is added to the gas in the tube. Curves F and H meet at the threshold point G, and the slope of curve H is much steeper than that of curve F. For temperatures entirely in the range of curve F or entirely in the range of curve H, the device of this invention will thus indicate the average temperature of the sensor. Although the etfect is the same in both ranges, the mechanism responsible is different in the two cases.

In the lower range, that of curve F, the operation of the sensor A obeys the ideal-gas laws except with the point of absolute zero temperature shifted to account for the volume of the responder sensor chamber. If part of the sensor is maintained at some temperature well below the threshold point G while the rest is heated to some higher temperature still below the threshold point G, the steady-state pressure in the sensor will be proportional to the average temperature of the sensor. That is, the increase in pressure resulting from heating part of the sensor will be a definite fraction of the increase in pressure which would result from heating the whole sensor uniformly, that fraction being the ratio of the length of the heated part of the sensor to the total length (if the sensor is a tube of uniform crons-sectional area) or the ratio of the free volume in the heated part of the sensor to the total free volume (if the sensor is not of uniform cross section).

As an example, suppose one-half of a sensor which is initially at a uniform temperature of F. is heated to a temperature of 500 F. (an increase of 400 F.) while the other half remains at 100 F. The increase in pressure will be one-half of that which would be measured if the whole sensor were heated to 500 F. Since the pressure-temperature relation, curve F, is a straight line, the actual increase in pressure is the same as the increase in pressure would be if the temperature of the whole sensor were increased by half as much, or to 300 F. But 300 F. is just the average temperature of the sensor when half is at 500 F. and the other half is at 100 F. Thus the device of this invention performs the desired averaging in the range below the threshold point G.

For temperatures above the threshold point G, the result is the same but the reason is different. When one part of the sensor is heated to a temperature above the threshold point G while the rest of the sensor remains at a lower temperature still above the threshold point G, the hydride in the heated part releases gas. Not all of the released gas contributes to an increase in pressure in the sensor, however, because some of the gas is taken up by the transducing agent in cooler parts of the sensor. As before, the actual increase in pressure is a definite fraction of the increase in pressure which would result from heating the whole sensor uniformly, that fraction being the ratio of the volume of the heated hydride to the total volume of hydride in the sensor. The end effect is that the pres- 13 sure increase in the sensor is directly proportional to the increase of the average temperature of the sensor, within a wide working range- The quantitative characteristics of the pressure-temperature curve for a given sensor depend upon several factors. The slope of curve F, that portion of the curve below the threshold point G, may be increased merely by increasing the amount of free gas within the sensor, and decreased by decreasing the amount of free gas within the sensor. The slope of curve H may be changed by the degree of ingassing to which the hydride is subjected before sealing off the sensor or by the choice of the type of hydride used. These latter factors also influence the position of the threshold point G.

-In order to make use of the averaging effect in the sensor of this invention, it is useful to provide a means of measuring the actual sensor pressure at any time. FIG. 22 shows a sensor A and responder B similar to those shown in FIG. 4. However, an additional tube 280 is sealed into a hole 281 so that the interior of the tube 280 is in communication with the sensor chamber 282 of the responder B. The other end of the tube 280 is sealed to an appropriate pressure measuring or hydrogen sensitive device 283, such as a gauge or any device sensitive to the concentration of hydrogen gas. The pressure measuring device 283 may be calibrated to read directly the average temperature of the sensor.

(3) The noble gases and the partial flam'e-ouLzest It might be though that an overcharge of hydrogen would be used to provide the desired free gas. However, at high temperatures hydrogen tends to diffuse through the walls of metal sensor tubes, reducing the charge and changing the characteristics of the sensor. Furthermore, there is another problem: Whether or not there is an overcharge of hydrogen there is a tendency for the hydrogen which is outgassed from a hotter part of the not-fully-ingassed filament 25 to re-ingas into another cooler part of the same filament 25, thereby lowering the over-all pressure below what it should be. Due to the great mobility of hydrogen, this transference of hydrogen from one part of the hydride to another is very rapid indeed, and it becomes difiicult, if not impossible, for such a device to pass a timed test known as partial flame-out, which is required by the FAA for airplane fire detectors.

These problems are solved, I have discovered, by incorporating a noble gas, preferably argon, inside the tube, which is evacuated of all other gases, including hydrogen except for what is contained in the hydride. With argon incorporated, the device easily passes the partial flameout test.

While argon is the preferred gas, a tracer of helium may be added to the argon, for use in leak detection during manufacture or at other times. Helium may be used, if desired, as the total overcharge, but its mobility is greater than that of argon, and so it is not so good as argon. Argon is less expensive than the other noble gases (neon, krypton, xenon), which is another advantage of using it. It is important to use as the overcharge a gas that is unable to be ingassed into the getter material in any substantial amount, and argon and the gases of its family do remain inert, nonreactive with the hydride core, and unable to diffuse through the walls of the sensor tube. Moreover, the use of the noble gases inside the tube as the gas averaging device for average temperature detection is advisable because these gases do not diffuse through the walls of the tube and thus make a very stable averaging system, which is not affected in the presence of high temperatures.

(4) Noble gas in the passage helps to prevent false alarms As an aid in assuring freedom from false alarms, it is desirable to have the inert gas overcharge set at a pressure of one atmosphere or somewhat higher. This prevents a change of pressure upon entry of additional gas from outside, if the tube does have a small leak, and it slows down considerably the entry of such atmospheric gas. Thus, the tire detector responds normally even after such a leak for a period of time that depends upon the size of the leak. If the tube interior were at a vacuum (that is, when the hydrogen is ingassed into the hydride), a leak would mean the entry of atmospheric gas that would raise the pressure inside the tube and, when the tube was heated, the additional gas present would further increase the pressure and might actuate the responder B at a lower temperature than that for which the device was originally set. Such actuation would be a type of false :alarm. By having the tube at exactly one atmosphere pressure, there is a balance which tends to keep the argon gas in the tube .and to mean that even if there is a leak and an exchange of gas, the actuation point would be substantially the same as before, or lower if there were leakage of gas out during the operation. In any event, there would be no false alarm. Further-more, if the pressure of the argon in the tube is set at a value greater than one atmosphere, the tendency for a false alarm is reduced, since it would take a higher temperaturethan normal to operate a device from which some argon had leaked out so as to reduce the pressure below its normal preset value.

(D) THE RESPONDING B AND THE WA'RNING CIRCUIT C Any pressure switch that is properly sensitive, has a small enough sensor chamber free volume, is sufficiently heat resistant, and has the needed connections, may be used as a responder B. However, I have invented a new pressure switch that is especially suitable for use herein. This switch is fully disclosed and claimed in a copending patent application, Ser. No. 86,252, filed Jan. 26, 1961. Moreover, in the present application certain features are brought out which result in a novel cooperation between the sensor and the responder.

(1) The responder 70 of FIG. 4

FIG. 4 shows one preferred form of responder B, comprising a unit 70 with two circular body members 71 and '72, preferably of non-porous metal, between which is bonded (as by brazing) a thin metal flexible disc or diaphragm 73. The body members 71 and 72 are hermetically sealed together and are in electrical contact for their full peripheries and over a substantial margin, but in the center the diaphragm 73 has a shallow generally spheri cal-segment depression 74 called a blister, which is free to move relative to the body members 71 and 72 and con stit-utes the active or movable part of the diaphragm 73. Use of a diaphragm 73 with a blister 74 makes possible the use of an upper body member 72 with a planar lower surface 75 and gives a more predictable response, but other diaphragm structures may be used where feasible. The lower body member 71 is formed with a shallow recess 76 in its upper surface, and the diaphragm 73 divides the resultant cavity between the body members into two regions or chambers 77 and 78. Of course, either body member 71 or 72 may actually be made by brazing together several thin plates of the desired configuration, and the recess 76 may be provided by using a stack of pre formed thin washers over a disc. Since the lower region 77 communicates with the sensor A, it may be called the sensor chamber. This sensor chamber 77 should be as small as possible. The other region 78 is located on the opposite side of the diaphragm 73 from the sensor A; so it may be called the anti-sensor chamber.

A preferred material for all the metal elements in the responder 70 is molybdenum or a suitable alloy thereof. There is good reason for having the entire responder, so far as the metal parts are concerned, made from the same metal, so that at high temperatures there will not be harmful differences in expansion. Moreover, since some tests by the United States FederalAviation Agency re- 1 5 quire that the responder, as well as the sensor, be able to withstand high temperatures, the diaphragm must be made from a metal whose qualities remain unimpaired by temperatures of at least 1000 F.

A very important qualification of the responder is that the portions exposed to the sensor interior not react with hydrogen even at quite high temperatures, so that snapaction of the diaphragm, for example, remains unaffected. Molybdenum is preferred because it answers these qualifications, and can be brazed at 2000 F. without having its strength substantially affected in an adverse manner. It should be noted, however, that pure molybdenum is too malleable to give a good snap action. Commercial molybdeu m (containing about 250 parts per million of carbon and containing other impurities) is or has been satisfactory, unless it is too pure. A molybdenum alloy containing small amounts (less than 1%) of titanium or of zirconium or of both is satisfactory. It does not react adversely with hydrogen, because it is 99% or better of molybdenum and the titanium and zirconium combine with any oxygen or carbon present in the metal to form oxides and carbides and so are no longer hydrogen getters.

As brought out many times herein, I utilize molybdenum metal in novel ways. For example, the molybdenum ribbon 26 succeeds where ribbons of stainless steel, nickel, maganese, iron, aluminum, copper, etc., failed, because they reacted with zirconium, titanium, etc. to form alloys with eutectic points below the melting points of the individual metals. In the operating range herein, molybdeumn solves the problem; it does not weld to the wire 25, or plug the gas passage, or form a low-melting-point alloy, and it gets stronger instead of weaker in the presence of zirconium and titanium. Again, this material is quite useful in the responder, as indicated above.

The end 30 of the sensor tube D is joined to and sealed to the lower body mmeber 71, being brazed to a short metal tube 79 that itself is prebrazed to the body member 71, fitting within a hole 80. The region 77 is closed and sealed except for its communication with the lumen of the sensor tube D. The interior volume of the sensor tube D is quite large compared to the chamber 77. Even the passage of the tube Dthe volume not occupied by the hydride and protecting substances-is many times larger than the volume of the sensor chamber 77. Generally, the sensor passage volume should be at least 50 times as great as the sensor chamber 77 volume. And the hydride should occupy about half of the total sensor inerior volumeabout the same as the sensor passage. For example, a typical sensor chamber 77 of this invention has a volume of 0.00057 cubic inch. A sensor A ten feet long has a typical passage volume of 0.03 cubic inch, and a twenty-five foot sensor A has a typical passage volume of 0.075 cubic inch-about 150 times that of the sensor chamber 77. These relative proportions are important to obtain the proper sensitivity to temperature changes, and the graph in FIG. 13 helps to illustrate them.

A tube 81 of nonporous ceramic material or other nonporous electrically-insulating material extends through an opening 82 in the upper body member 72 and is hermetically sealed in place there with its lower end 83 flush with the bottom surface 75 of the body member 72. The hole 82 and tube 81 are preferably centered with respect to the blister 74, on the anti-sensor side thereof. A metal electrode 84 is located inside and joined securely to the tube 81 at the end 83 nearest the blister 74, with a portion 85 of the electrode 84 extending a very short distance below the lower surface 75 of the body member 72. The amount by which the portion 85 extends below the surface 75 is carefully controlled so as to be uniform in each responder of any particular design. This geometry means that the blister 74 can make electrical contact with the electrode portion 85 when the blister 74 is forced up by pressure in the sensor chamber 77.

As shown, the electrode 84 may be a solid rod only slightly smaller than the lumen of the tube 81, in order to give good uniform contact with the blister 74 at that time and also to afford communication between the chamber 78 and the inside 86 of the tube 81. A conducting wire 87 extends from the electrode 84, preferably along the axis of the tube 81, and is brought out of the tube 81 through a hermatic seal at a sealing cap 88. The tube interior 86 and the anti-sensor chamber 78 thus .are part of the same enclosure.

If sufficient pressure is applied to the sensor side of the blister 74, the blister will deflect and make contact with the electrode portion and if the deflecting force is removed, the restoring force of the blister 74 will return it to its relaxed position and thus break contact with the elec trode portion 85. The force necessary to do this may be chosen by proper design of the blister to accommodate a wide range of values.

(2) A simple circuit C and its operation (FIG. 4)

As explained before, the responder B may be connected to an alarm circuit C which, as shown in FIG. 4, may be a simple visual indicator consisting of a lamp 90 in series with the conducting Wire 87 and a source 91 of electrical current, which may be a battery, as shown, or may be a source of alternating current. A return path for the electrical circuit C may be provided by grounding either one of the plates 71 or 72 and is shown as a ground wire 92 in FIG. 4.

In operation, when a portion of the sensor A is exposed V to heat at a level high enough to cause the transducing agent E to rise above its threshold temperature G gas is liberated. This gas cannot escape from the sensor tube D except into the sensor chamber 77, where it exerts pressure upon the blister 74. This pressure tends to move the blister 74 away from the lower body member 71 and toward the upper body member 72. The pressure in the sensor chamber 77 is a function of the temperature of the sensor A, and in general there will be a rise in pressure corresponding to each incremental increase in temperature of the sensor A above the threshold temperature G. This pressure, if great enough, will cause the blister 74 to make contact with the electrode 84, but no contact 'will be made unless the temperature of the sensor A is at or above a de finite level. Similarly, a rise in the average temperature along the complete sensor A causes a rise in pressure of the noble gas therein, which is also capable of operating the responder B.

When the sensor A is exposed to heat at a level high enough to cause the blister 74 to make contact with the electrode 84, current flows from the battery 91 through the lamp 90, the conductor 87, the electrode 84, and the blister 74 to the body members 71 and 72 and returns to the battery 91 through ground line 92. This current flow causes the lamp 90 to light and provides a visual indication that the temperature of the sensor A is at or above a certain level. When heat is removed from the sensor A, the transducing agent E cools and reabsorbs its previously liberated gas, resulting in reduction of the pressure exerted upon the blister 74. Cooling also reduces the pressure resulting from the presence of the noble gas. The blister 74 moves away from the electrode 84, breaking the electrical circuit, and the lamp 90 goes out.

In practice, the sensor A is placed in the area (see FIGS. 1 and 2) whose temperature is to be monitored, while the responder B may be located upon or on either side of a shielded wall or at some easily accessible area. Thus only the sensor A itself need be exposed to possible heat sources, and it contains no element of the electrical warning circuit. In this manner, protection for the responder B and its associated alarm circuit C may be provided.

(3) Some ways of setting the threshold temperature. Still other significances of inert gases (FIG. 4) The force necessary to deflect the blister 74 against the electrode 84 can be chosen to accommodate a wide range 17 of values by a suitable choice of mechanical parameters. Once this force is determined, the dimensions of the sensor tube D and the amount of transducing agent E may be chosen by design to provide the force necessary to obtain contact between the blister 74 and electrode 84 at a certain temperature.

In addition to mechanical design considerations, the necessary deflecting force may also be altered by precharging the anti-sensor chamber 78 with a gas under pressure or by partially evacuating it. To accomplish this, gas is forced into (or withdrawn from) the tube 81 after its attachment to the body member 71 and before it is closed by its cap 88. The required deflecting pressure against the blister 74 becomes greater as more gas is present in the chamber 78.

Alternatively, the deflecting pressure may be effectively lowered by precharging the inside of the sensor tube D and the sensor chamber 77 with gas. In this case, if the ambient pressure in the sensor chamber 77 is greater than normal, less than normal gaseous liberation from the transducing agent E is required to deflect the blister 74 against the electrode 84. Most gases may be employed for this purpose; however, ideally the gas should not react chemically with its surrounding materials. Particularly suitable are the inert gases, such as helium, argon, neon, and xenon, especially since they do not readily diffuse through most materials. As a consequence, a precharged pressure of argon, for example, may be maintained for an indefinite length of time to retain a desired biasing of the diaphragm 73, as described.

Biasing in the anti-sensor chamber 78 is important because the diaphragm 73 naturally has a temperature coefficient of expansion which tends to make the diaphragm become easier to flex as it gets hotter. This tendency can be counteracted so that even when the diaphragm 73 reaches 1000 F. or more, it operates at exactly the same sensor pressure as when it is cool. Or it can be made to become more resistant as the temperature rises, if that is desired. Generally, uniformity is desirable and is obtained by having the anti-sensor chamber 78 at a greater pressure than the sensor chamber 77. For example, if the sensor is loaded with argon at one atmosphere pressure (15 p.s.i.a.), the anti-sensor chamber 78 may be filled with argon at 23 p.s.i.-a.

(4) The responder of FIG. 12 and its modified circuit C In place of the responder operating with a normally open circuit, it may operate with a normally closed circuit. Thus, the sensor A may have a short terminal portion 94 extending into the recess 76 and in normal contact with the blister 74. At the critical pressure (resulting from exposure of the sensor A to a critical temperature) the blister 74 moves away from and breaks contact with the sensor portion 94.

In this form of the invention the sensor A may be grounded at 95, and it may be insulated from the responder body by an insulator 96. The battery 91 may be connected to the responder body through a load resistor 97. The warning lamp 90 may be in parallel with the sensor A and grounded at 98.

During stand-by conditions the lamp 90 is not lighted because the current passes almost exclusively through the low-resistance path to ground, via the responder B, blister 74, sensor terminal portion 94, sensor tube D and ground 95 back to the battery 91. When the pressure in the sensor A and sensor chamber 77 actuates the diaphragm 73, the blister 74 moves away from the terminal 94. Then the low-resistance shunt is broken, and the only return path for the current from the battery 91 is through the lamp 90 to the ground 98. Thus, once again, exposure of the sensor A to a critical temperature gives a warning.

() A more complex form of responder B and its associated circuit C (FIG. 14)

(a) Description of the responder 120 and its circuit.- When it is desirable to provide an indication of two or 18 more heat levels within the same area, the arrangement shown in FIG. 14 is highly desirable. In addition, FIG. 14 shows a test device that enables the operator to determine whether the unit is functioning properly.

In FIG. 14 the sensor A is joined to a responder at the lower of its two circular metal body members 121 and 122. The lower body member 121 is recessed to provide a cavity for a sensor chamber 123, and a thin, flexible metal diaphragm 124 is sandwiched between the body members 121 and 122 and brazed to them in an hermetic seal. The metal elements 121, 122, and 124 may be molybdenum, Kovar, or Phosphor bronze, for example. The diaphragm 124 is provided with two generally spherical depressions or blisters 125 and 126, isolated from each other by a portion 127 brazed or otherwise hermetically bonded to the body member 122.

Three ceramic or other non-porous and electrically nonconducting tubes 130, 131, and 132 are sealed into and extend through openings in the upper body member 122. The interior 133 of the tube 132 extends through a hole 134 in the diaphragm 124 directly into the sensor chamber 123, while the tubes and 131 are centered directly above their respective blisters 125 and 126 and open into separate anti-sensor chambers 135 and 136. Electrodes and 141 at the lower ends of the tubes 130 and 131 extend slightly below the tubes 130 and 131 and the upper body member 122, so that the blisters 125 and 126 can each be deflected into contact with them. Conducting wires 142 and 143 from the electrodes 140 and 141 respectively extend axially through the tubes 130 and 131 and emerge through sealing caps 144 and 145.

The interior 133 of the tube 132 is filled with a heatdissociable material 146 such as palladium hydride granules (see FIG. 8), and a generally axially extending filament 147 is embedded in this material and extends out of the lower end of the tube 132 through a small plug 148 and terminates on the lower plate 121 at a ground point 150. The plug 148 serves to retain the hydride 146 within the tube 132 but allows any gas that may be liberated from the material 146 to pass from the tube 132 into the sensor chamber 123. The upper end of the filament 147 is brought out of the; tube 132 through a sealing cap 151 and is joined to a conducting wire 152.

The diaphragm 124 and its blisters 125 and 12 6, together with the peripheral bond 127 between and the bond around the blisters, efiectively provides three chambers: the interior 133 of the tube 132 and the interior of the sensor tube D enjoy a common atmosphere with the sensor chamber 123 to the exclusion of any other atmosphere. On the other side of the diaphragm 124 are the two mutually exclusive anti-sensor chambers 135 and 136.

Just as in the device of FIG. 4, the force necessary to deflect the blisters 125 and 126 into contact with the electrodes 140 and 141, respectively, is a function of the mechanical design of the blisters, and may be chosen so that each blister 125 and 126 requires the same or a different deflecting force. In addition, this force may be changed to any desired value by precharging any of the chambers 123, 135, and 136 with an inert gas. For example, the sensor A may be heated to a desired operating point, e.g. 800 F., filled with argon at the predetermined operating pressure and sealed 0E. The tube 130 is then filled with argon at room temperature at a pressure just sufficient to cause the blister 125 to touch its electrode 140, and the tube 130 is then sealed off. Next the sensor A is cooled to a second desired operating temperature, say 400 'F., and the tube 131 is filled with argon at room temperature at a pressure just sufiicient to cause the blister 126 to touch the electrode 141, and the tube 131 is then sealed off.

The conducting wires 142, 143, and 152 are part of an alarm circuit C. The conductor 152 passes to two normally o-pen parallel test switches 153 and 154, a resistor 155 being in series with the test switch 154. From the switches 153 and 154 lines 156 and 157 lead to a main line -158, which leads to a suitable AC or DC current source, such as a battery 160. The conductor 143 is connected to a signal lamp 161, which is connected by lines 162 and 163 to the main line 158. The conductor 142 is connected to a signal lamp 164, which is connected by lines 165 and 163 to the main line 158. The conductor 142 is also connected by a line 166 to a normally closed bell-ringing circuit 167, which might either be an AC or DC type, depending upon the current source 160, and is connected to the main line 158. Although a bell 168 is shown in the circuit 167, various other devices may be substituted for it, such as a buzzer or a relay.

(b) Operation of the device of FIG. Z4.-Assume, by way of illustration, that the sensor A, the blisters 125 and 126, and other parts are so constructed that the blister 125 will make contact with its electrode 140 when the sensor A is exposed to a fire temperature, and so that the blister 126 will make contact with the electrode 141 when the sensor A is exposed to an overheat condition substantially lower than fire temperature. For example, the fire temperature may be 450 C. and the overheat temperature may be 200 C.

Then, if the sensor A is exposed to an overheat condition of 200 C. or higher, gas from the sensor A increases the pressure within the sensor chamber 123 and deflects the blister 126 against the electrode 141. However, the blister 125 will not contact the electrode 140. Current thus flows from the battery 160 through the lines 158, 163, and 162, the lamp 161, the conductor 143, the electrode 141, the blister 126, and the body members 122 and 121, to ground through the point 150. The resulting illumination of the lamp 161 provides an indication that the temperature of the area in which the sensor A is located is at or above the critical over-heat temperature but is still below the fire temperature.

When the sensor A is exposed to the fire temperature of 450 C., more gas comes from the sensor A and deflects the blister 125 against its electrode 140. The blister 126 is still in contact with its electrode 141 and its lamp 161 is still lighted. But new current from the current source 160 also passes through both the lamp 164 and through the bell circuit 167, ringing the bell 168 and lighting the lamp 164. This provides a visual and audible indication of a fire condition in the area to which the sensor A is exposed.

If the fire is put out and the sensor A is cooled, the pressure on the blisters 125 and 126 is lowered to break their contact with their electrodes 140 and 141. The current flow then stops, the lamps 161 and 164 go out, and the bell 168 stops ringing.

(c) The test circuit FIG. 14 and its operation.The circuit segment consisting of the parallel arrangement of test switches 153 and 154 in series with the conductor 152 and filament 147 provides a convenient arrangement for checking the operability of the devices. As explained previously, the amount of gas liberated from heat-dissociable material, such as the hydride 146 contained in the tube 132, is a function of its temperature, and this in turn is a function of the amount of current through the filament 147. The hydride 146 is of a type that ingasses at a temperature lower than the ingassing temperature of the hydride in the sensor A. As a result, it will re-ingas its own hydrogen, and the sensor operation will not be affected by a test. Palladium hydride may be used as this material 146 when the sensor hydride is of vanadium, titanium, or zirconium.

Upon closure of the test switch 154, current flows from the current source 160 through the lines 158 and 157, the switch 154, the current-limiting resistor 155, and the conductor 152, to the filament 147 and thence to the ground point 150. The resultant heating of the hydride 146 liberates hydrogen therefrom and, since the gas cannot escape from the sensor chamber 123, it exerts pressure on the sensor side of the blisters 125 and 126. The mag nitude of the current-limiting resistor 155 is chosen so that the amount of gas liberated from the hydride 146 is sulfi- 20 cient to deflect the blister 126 against its electrode 141 but insuflicient to deflect the blister against its electrode 140. The result is that the lamp 161 is illuminated, thus providing an indication that the overheat portion of the circuit is functioning correctly and that the sensor A and sensor chamber 123 do not leak.

It, now, the test switch 153 is engaged, a larger current flows through the filament 147, due to the absence of a resistor between the current source and the filament 147. The increased current heats the hydride 146 to a higher temperature, with the result that more hydrogen is liberated. Assuming that the circuit parameters and the amount of hydride are chosen correctly, enough pressure can be exerted upon the blister 125 to deflect it against its electrode 140, ringing the bell 168 and lighting the lamp 164, indicating that the fire portion of the circuit is functioning correctly and also testing the sensor A and chamber 123 against leaks. When the switches 153 and '154 are disengaged, current flow through the filament 147 ceases, and the hydride 146 cools, re-ingassing its previously liber ated hydrogen. The pressure in the sensor chamber 123 drops, and contact between the electrodes 140, 141 and the blisters 125, 126 is broken, resulting in the extinguishment of the lamps 161 and 164 and silence of the bell 168.

(d) Disposition of the unit-As with the device of FIG. 4, only the sensor A need be exposed to the area whose temperature it is desired to monitor. The responder 120 and the alarm circuit C may be located in a readily accessible or convenient area. For example, as shown in FIG. 16, if it is desired to monitor temperatures Within an engine nacelle of an aircraft 171, only the sensor A need be located within the macelle 170, while the responder B and alarm circuit C may be located behind a fire wall 172, with the lamps and switches on an instrument panel 173, where the pilot can see them. This provides a distinct advantage in that no electrical circuits need be located in an area where conditions adverse to their operation might prevail. In addition, accidental damage to the sensor A can in no way set off a false alarm, as is evident from its construction.

Although only two blisters 125- and 126 are shown in FIG. 14, more, each with its own alarm circuit, may be placed in a responder B to provide indications of several additional temperature conditions, and their omission is not intended to exclude them from the scope of the invention.

It will be noticed that a fire detector using the principles of this invention can be made very light in weight. The sensor A is a small tube with very low weight per unit length and the responder B is also quite small and light. The only additional elements in the system are the warning lights and the circuit wiring which can also be made very light weight. A fire detector system consisting of a 25-foot sensor, responder, and indicating lamps (exclusive of the wiring itself) can be made to weigh less than eight ounces-a small fraction of the weight of other fire detector systems. This fact gives this invention an obvious advantage in aircraft fire-detector installations wherein weight must always be kept to a minimum.

(e) A mounting for the transducer 120 (FIG. 15).- FIG. 15 shows one way in which the plural blister responder 120 of FIG. 14 may be conveniently mounted so that removal and replacement of the sensor A and responder B are relatively simple. In FIG. 15 the responder 120 is mounted to a fire wall 172 by means of a main body 174 and a cap 175. The main body 174 has a flange 176 that may be mounted to the wall 172 by rivets 177 or by bolts or other suitable means. The responder body members 121 and 122 fit snugly within a well 178, provided by two offset cylindrical portions 179 and 180 and a shoulder 181, all on the main body 174. The largerdiameter cylindrical portion 180 has an exteriorly threaded portion 182 on which the cap may be screwed. The plate 122 is sealed to the well 178 by means of an O- ring gasket 183 or other such seal. Thus the responder 120 is held tightly in the well 178, and gas or vapor cannot leak from one side of the fire Wall 172 to the other side.

The cap 175 is provided with a central axial hole 184, through which the sensor tube D may pass during assembly. The well 178 is designed a little shallower than the thickness of the responder 120, so that the lower edge 185 of the lower body member 121 projects slightly below the lower edge 186 of the main body 174; so when the cap 175 is screwed tightly onto the main body 174 it necessarily still contacts the responder body member 121 and cannot touch the edge 186 of the body 174. Therefore, it compresses the responder 120 against the gasket 183. This arrangement also assures good electrical contact between the cap 175 and the responder plates 121 and 122, especially at the ground point 150, so that the ground point for the system may be taken off either the cap 175 or the main body 174.

The upper portion 179 of the main body 174 is made spacious enough so that, upon assembly of the responder 120 into it, the caps 144, 1-45, and 151 pass in freely without contacting the side wall 179. At the upper end of the main body 174 a threaded portion 187 is provided to fit a suitable connector by means of which the necessary connections between the external alarm circuit C and the conductors 142, 143, and 152 are made. This may conveniently be provided, for example, by means of a wellknown type of threaded amphenol fitting (not shown).

Installation and removal of the responder 120 from this mounting is a simple matter. For installation, all that need be done is to unscrew the cap 175 from the main body 174, insert the responder 120 into the well 178, slide the cap 175 over the sensor A through the hole 184, and screw the cap 175 on the threaded lower end 178 of the main body 174. The electrical fitting (not shown) then may be assembled to the conductors 142, 143, and 152 by screwing it onto the threaded portion 187 of the main body 174. Removal is as simple.

The parts 174 and 175 are preferably constructed of metal that gives good electrical contact between the cap 175 and the lower plate 171. However, this is not necessary. An equally feasible method would be to construct the fitting of an insulator and provide a ground lead line for the direct connection from either the lower or upper body member 121 or 122.

(6) An aircraft system that indicates both overheat and fire and also actuates a fire-extinguishing system (FIGS. 16 and 17) FIG. 16 shows a sensor A placed in an engine nacelle 170 of a typical turbo-jet airplane 171. The responder 120 is mounted on the fire wall 172 and may signal the cockpit through the conductors 142, 143, 152. The conductor 142, associated with the fire alarm circuit as in FIG. 14, is here connected in series with an electrically-operated; normally closed solenoid valve 190' which, when actuated, discharges a sphere 191 of fire-extinguishing chemical, such as Freon 13B-1, through lines 192 and spray-nozzles 193 into the engine nacelle 170. The view is diagrammatic, rather than to accurate scale.

Overheat conditions are distinguishable from fire, and a partial view of the dashboard 173 that faces the pilot is shown in FIG. 17, where the overheat-warning light 161, the fire-warning light 164, the fire bell 168, and the test switches 153 and 154 are shown.

When fire occurs in the engine nacelle 170, the heated sensor A causes the responder 120 to react and send current to pass through the fire alarm conductor 142. This current actuates the electrically-operated valve 190 and sends fire-extinguishing fluid to the spray-nozzles 193. In addition, the current lights the lamps 161 and 164 and rings the fire bell 168. At high temperatures below fire temperature, the simple overheat-warning light 161 is lighted. Here, again, the unit is small and light in weight and is easily installed.

(7) Several responders B in one alarm circuit C (FIG. 18)

FIG. 18 shows several plural-blister units of the type depicted in FIG. 14, grouped electrically and mechanically. This arrangement makes it possible for one compact alarm circuit C to monitor temperatures within several areas. In addition, provision is made so that each of the responders 120 may be tested individually or simultaneously. In this arrangement, each sensor A of the four responders 120a, 120b, 1200, and 120d may, for example, be located within a different engine nacelle or within the same engine nacelle but at different locations, thereby providing indication of both overheat and fire conditions within their respective areas.

The responder 120a has three conducting-wires 200, 201, and 202; the responder 12% has wires 203, 204, and 205; the responder 120c has wires 206, 207, and 208; and the responder 120d has wires 209, 210, 211. The conductors 200, 203, 206, and 209 are for fire warning, while the conductors 201, 204, 207 and 210 are for overheat warning, and the conductors 202, 205, 208 and 211 are the test leads.

The test wires 202, 205, 208, and 211 are all connected in parallel with each other to a lead 212 which connects that all to lead lines 213 and 214. Each lead 213, 214 has a variable resistor 215 and 216 in series with a switch element 217, 218, respectively, and with a main line 219 that is connected to an AC or DC power source 220.

Each conductor 200, 201, 203, 204, 206, 207, 209, and 210 leads to a respective indicator-lamp 221, 222, 223, 224, 225, 226, 227, and 228. These lamps are joined in parallel to the main line 219 and thereby are connected to the power source 220. A single bell circuit 230 is connected to the line 219, in parallel with the lamps, and by a lead 231 to each fire conductor 200, 203, 206, and 209 by means of rectifiers 232, 233, 234, and 235. The rectifiers 232, 233, 234, and 235 keep all the fire-warning lamps 221, 223, 225, and 227 from lighting except when actually exposed to a fire condition or a test therefor. Without the rectifiers, a fire indication in any one conductor 200, 203, 206, or 209 might light the lamps in all. A condenser 236 may be connected between the line 231 and ground to prevent arcing in the responders. The value of the condenser 236 may be, for example, 0.002 microfarad.

Operation is the same as in FIG. 14. Each sensor A acts individually through its individual responder B to affect its individual warning light in the single circuit C and to ringthe sole bell. The test circuits likewise operate as in FIG. 14, with the exception that the anti-sensor sides of each responder 120a, 120b, 120e, and 120d may be pressurized at different levels, and the variable resistors 215 and 216 enable the two switch elements 217, 218 (or even one single switch element) to check all circuits. As the current through the test filaments is increased by slowly decreasing the resistance of the variable resistor 215 or 216, each responder is actuated in turn, starting with the one set for the lowest temperature. The variable resistors may be calibrated to read directly the equivalent temperature to which each responder responds. In the event that all of the sensors A and responders B in the circuit C are of identical design, and are identically pressurized, then only one setting of each resistor 215, 216 need be made, and it can be made prior to actual operation so that, when the switch 217 is engaged, all of the lamps 222, 224, 226, and 228 associated with the overheat portions of the circuit are illuminated, thereby insuring that the overhead circuits are functioning correctly, and so that when the switch 218 is engaged all the firewarning lamps 221, 223, 225, and 227 are illuminated. The rectifiers are required whether the power source 220 is AC or DC.

Although but four units are shown in the arrangement of FIG. 18, obviously more may be added or extended as desired, and each responder may be inserted into a fitting of the type shown in FIG. 15. For example, each sensor A may lead to one engine nacelle of a multiengine aircraft, while each responder B may be mounted in the type of fitting shown in FIG. on the fire wall of its engine. Then, the electrical circuit may be conveniently connected and arranged into a very compact unit on the operator-side of the fire wall,

(8) Variation of the pressure in the antiserum chamber (FIG. 19)

As explained before, the force necessary to deflect a blister onto its respective electrode is a function of the pressure in the anti-sensor chamber. A way of changing this pressure is shown in FIG. 19, which is an enlarged view of a portion of a simplified responder 239 generally like the responder 70 shown in FIG. 4, identical numerals being applied to those parts that are identical. In addition, however, the responder 239 has a porous tube 240, which may be of porous ceramic mounted inside the tube 81 by brackets 241. The tube 240 contains a selected amount of a suitable heat-dissociable material 242, for example, vanadium hydride. Embedded in the hydride 242, which preferably is treated as described in my copending application Ser. No. 65,891, filed Oct. 31, 1960, is a filament 243. Leads 244 and 245 for the filament 243 are brought out of the tube 240 through caps 246 and 247 and then pass through the walls of the tube 81 to a potentiometer 248 and a battery 249. The points where the conductors 244 and 245 are brought out through the tube 81 are sealed so that, as before, the interior 86 of the tube 81 and the anti-sensor chamber 78 enjoy a common atmosphere to the exclusion of any other.

Now, in addition to the mechanical design of the system which includes the design of the blister 74, the effective force necessary to deflect the blister 74 against the electrode 84 may be altered by sending current from the battery 249 to the filament 243 through the potentiometer 248. The magnitude of this current depends upon the setting of the potentiometer 248, and the current through the filament 243 determines the amount of gas liberated from the hydride 242. This released hydrogen passes through the porous tube 240 and increases the pressure in the anti-sensor chamber 78, exerting a force against the blister 74 that tends to counteract the deflecting force due to pressure in the sensor chamber 77. The higher the pressure in the anti-sensor chamber 78, the more the pressure that has to be generated in the sensor chamber 77 to deflect the blister 74 against the electrode 84. By altering the setting of the potentiometer 248, the effective temperature to which the responder 239 as a whole will respond may be continuously altered within the design range of the system, to respond to any of many levels of temperature. For example, suppose that the responder 239 is initially set to respond to a temperature of approximately 1500 F. If it is desired that the responder 239 not respond until the temperature reaches 2000= F then the resistance of the potentiometer 248 is decreased so that more current flows through the filament 243, and a greater biasing force is applied to the blister 74 in the anti-sensor chamber 78. By means of a calibrated potentiometer 248, the ranges of temperature may be detected.

This design increases the adaptability of the responder to many situations. The responder-sensor combination may be used to monitor a certain temperature within a certain area and, when this is completed, the unit may be removed and, by adjusting the potentiometer 248 to a previously calibrated setting, it may then be inserted into another area to monitor a difl erent temperature level. This design obviously can be employed in either or both tubes of a plural-blister responder like that of FIG. 14. Moreover, when the current through the filament 243 is cut off, the responder 239 functions just like the responder 70 of FIG. 4.

24 (E) INDICATION OF SPOT TEMPERATURES The foregoing discussion of the averaging effect of the sensor of this invention assumes that the entire sensor is either above the threshold point G or below the threshold point G. It is not ditficult to imagine situations wherein this condition is not satisfied, for example, where a local high-temperature fire exists at one small region of the sensor while the rest of the sensor is at a much cooler ambient temperature. In such a situation where all but a small part of the sensor is below the threshold point G, an interesting and extremely useful effect is observed.

Since the curve H is so steep (the ratio of the slopes of the curves F and H may be 150 or more), it is not necessary to heat the sensor very much above the threshold temperature (the temperature at the threshold point G) to produce quite high pressures in the sensor. With the responder of a heat detector like that shown in FIG. 4 set to respond at a given pressure in the vicinity of the threshold pressure (the pressure at the threshold point G), it is not necessary to heat even a small part of the sensor very much above the threshold temperature to cause the sensor to rise high enough to actuate the responder. It will be seen that the temperature at which actuation ocours is very sharply defined and close to the threshold temperature, and is only slightly affected by the amount of the sensor which is heated. This insensitiveness of the operating temperature to the amount of sensor heated is a very important feature in a fire detector and is a direct result of the extreme steepness of the pressure-temperature curve above the threshold point G.

It may be remarked that the separate functions, averaging and sensitivity to local heating above the threshold temperature, are independent. The internal pressure of the sensor is always a measure of its average temperature and the provision for sensitivity to local heating does not change this fact. Thus this invention provides for two independent functions in one device with one sensing element. This accomplishment has not previously been achieved in the design of heat-detecting instruments.

The sharp change in internal pressure at the threshold point G may be used to indicate local temperature conditions. For example, using the system of FIG. 14, suppose that zirconium hydride is employed as the transducing agent E. The blister may be designed to deflect against the electrode under a pressure of 25 p.s.i.a. in the sensor chamber 123; and the blister 126 may be made to deflect against its electrode 141 under a pressure of 20 p.s.i.a. in the sensor chamber 123. The volume of the tube D, the amount of the transducer agent 13, and the initial precharge pressure of gas (e.g., argon) may be chosen to correspond to a threshold point G of 1030 F. producing a 25 p.s.i.a. pressure. This temperature corresponds to fire conditions. Thus, when the sensor A is exposed to heat below the 1030 F. level, the internal pressure and temperature obey the linear relation corresponding to curve F of FIG. 11. The diaphragm blister 125 will also be actuated by an average sensor temperature of, say, 500 F., when all points thereof are below the outgassing threshold temperature G.

As the temperature is raised from the ambient atmospheric temperature, though still well below 1030 F., eventually an average temperature will be reached at which the average internal pressure inside the sensor A equals 20 p.s.i.a. At this temperature, which may be 300 F., the blister 126 is deflected onto its electrode 141 and energizes the lamp 161. The blister 126 will also be deflected at, say, 1000 F. by the outgassing hydride if even a few inches of the sensor are at this temperature. Thus, when the lamp 161 lights, it indicates an average sensor temperature of 600 F. or a discrete temperature of 1000 F.

Sharper detection of the threshold point G is obtained by eliminating the inert gas and operating the agent E under vacuum conditions, thereby making it possible to detect a threshold temperature applied to only a short 25' length of the tube D. As before, choice of the agent E, its degree of ingassing, and the sensitivity of the responder B may be varied to changethe threshold point G. Alloys of agents E may be used.

(F) USE OF SENSOR WITH DISCONTINUOUS TRANSDUCING AGENT (FIGS. 20 AND 21) The sensor elements A described heretofore have been of the type in which the transducing agent E is distributed substantially uniformly and continuously throughout the sensor tube D. However, this is not always essential and in some cases it may be preferable to have the transducing agent E discontinuous. Two types of such structure are shown in FIGS. 20 and 21.

In FIG. 20 a transducing agent E like that of FIG. is shown contained in a tube 250. Thus there are shown three portions 251, 252, and 253 of the transducing agent E, each like that of FIG. 5. The portions 251 and 252 are separated from each other by a restrictive portions 254 of the tube 250. The restriction prevents relative movement of the elements 251 and 252 in the tube 250 and also provides a passage 255 of small diameter, so that the volume of the connection portion 254 is not too large relative to the small clearance area around the transducer agent portions 251, 252, and 253 in larger portions 256, 257, and 258 of the tube 250. The restriction may be provided by welding a section of narrower-diameter tube to the main tube or by inserting a narrower-diameter tube. By way of example, a section 259 is also shown, connecting the elements 252 and 253; in this section there is no restriction, but there is a dummy wire\259a, which may be of molybdenum. This type of structure may be used where it is desired to use a single transducer A to test the temperature level of three different locations and where there is no need or desire to test the temperature level in between these locations. By making the tube diameter of the connecting portions 254 and 255 very small, these portions may be very long, if that is desired, without unduly aifecting the operation of the device.

FIG. 21 shows an example of a different type of installation comprising a sensor tube 260 in which three different types of transducing agents 261, 262, and 263 are used. The agents 261 and 262 are spaced apart from each other, and the agent 263 is spaced from the responder B by tube portions 264 in which there are dummy wires. The agents 262 and 263 are spaced from each other by a narrowdiameter tube 269. The transducers 261, 262, and 263 are in tube portions 266, 267, and 268. The portion 261 of transducing material may, for example, be a titanium hydride wire 270 with a ribbon 271 of tungsten wound around it; the portion 262 may be pellets 272 of vanadium hydride; While the portion 263 may comprise chunks 273 of tantalum hydride with passage means left between them. This means that the three tube portions 266, 267, and 268 may be located. at places where the temperature responses are different. Since the three hydrides will outgas at different threshold points and since the volumes which they outgas are different, it is possible to make practically any adjustment that may be desired. Alloys of the materials may be used to get still different combinations or to vary the temperature response characteristics within practically any desired range. The tube 260 may be evacuated to give sharp response in those areas, or it may be filled with a suitable inert gas so that the entire tube 260 is still capable of giving response to average temperatures below the threshold points of the hydrides. This form of the invention serves as an example of how the variation may be made, but of course other variations may also be made, as will be apparent to a man skilled in this art.

The averaging characteristics of the sensor when using a gaseous overcharge (e.g., argon) are influenced by the distribution of free volume along the sensor (or, what is equivalent, the cross-sectional area at any point along the sensor). If the free volume is constant or uniform along the sensor, then the unit will respond to the true (arithmetic) average temperature (below the outgassing temperature of the getter) of the sensor. However, it is possible to weight the average in favor of a particular section of the sensor merely by increasing the free volume in that section. The temperature of that section will then have a greater influence on the pressure in the sensor (and hence on the response) than that of other parts of the sensor. This effect is useful, for example, where one wants to monitor the over-all temperature of an electric motor but is especially concerned that the bearings do not overheat; the part of the sensor near the bearings would be made with a greater free volume sothat any overheating there would be noticed even though the over-all average temperature was not unduly high. Conversely, the average can be weighted the other way merely by reducing to negligible values the free volumes in the sections of the sensor where restricted response is desired. Note that none of these changes has any effect on the response to flame when the getter outgasses. The changes in free volume may be made by changing the inside diameter of the sensor tube, by changing the size of the getter or dummy wire, or in other ways.

(G) FULFILLMENT OF FAA QUALIFICATIONS This invention enables fulfillment of the rigid Federal Aviation Agency qualifications which heretofore were not fulfilled. Rather than going through each test required, a few of the important outstanding ones will be considered.

(1) Response time test The FAA standards require exposure of a 6" length of a continuous type sensor to a test flame of 1100 C. (approximately 2000 F.), starting from room temperature. The response time is not to exceed five seconds.

A sixinch section of the sensor of a unit of this invention which had previously undergone three one-minute exposures to a totally enveloping 2000 F. flame was exposed to a 2000 F. flame from a standard fire detector test burner. The unit signalled an alarm in 3.5 seconds. After removal from the flame, the unit cleared the alarm in 1.5 seconds.

Another unit of this invention which had not been exposed to a totally enveloping flame was given a similar response time test. With the six inches of the sensor in a 2000 F. flame from a standard fire detector test burner, the unit signalled an alarm in 2.6 seconds. After removal from the flame, the unit cleared the alarm in 2.5 seconds.

(2) F alre alarm due to rate of temperature change In accordance with the FAA standards, a six-inch section of the sensor of a unit of this invention was inserted quickly into a l000 F. flame from a standard fire detector test and .left there for one minute. No alarm was signalled. The rate of temperature rise was in excess of 10,000 degrees per minute for the first five seconds and zero thereafter.

A six-inch section of the unit was then exposed to a temperature which rose from F. to 1000 F. in one minute. No alarm was signalled. The rate of temperature rise was about 900 degrees per minute for a duration of one minute.

The entire sensor and responder of the same unit were placed in an air furnace which had been preheated to 400 F. and left there for one minute. No alarm was signalled. The rate of temperature rise was initially in excess of 400 per minute, tapering off to zero by the end of one minute.

The sensor and responder of this unit were then placed in an air furnace at 250 F., and the temperature of the furnace was raised at a rate of about 50 per minute for a duration of three minutes. No alarm was signalled.

(3) False clearing of alarm due to partial extinguishment The standards set a test in which the test flame shall be applied for 30 seconds. The test flame shall then be 27 masked so as to reduce its effective area of approximately 50 percent. The alarm signal shall not clear. After an additional 30 seconds, the flame shall :be removed entirely and the alarm signal shall clear within 30 seconds.

A. six-inch section of the sensor of a unit of this invention was exposed to a 2000 F. flame from a standard fire detector test burner. An alarm was signalled in 3.0 seconds. After 30 seconds in the flame, the area exposed to the flame was reduced to approximately three inches and was left in the flame for another 30 seconds. The alarm did not clear. After removal from the flame, the unit cleared the alarm is about one second.

(4) Vibration The FAA also has standards relating to false alarm occasioned by vibration and the ability to give a true alarm during and after vibration.

A unit of this invention was vibrated for 137 hours at an amplitude of 0.25 inch and a frequency of 330 cycles per second and for an additional 130 hours at an amplitude of 0.10 inch and a frequency of 330 cycles per second. No resonant frequency had been detected for any part of the unit. No false alarm occurred during the test. While the unit was being vibrated, a four-foot section of its sensor was exposed to an alcohol flame at a temperature of 1050 F. The unit signalled an alarm in four seconds and, after removal from the flame, the unit cleared the alarm in two seconds. At the conclusion of the vibration test, the unit was inspected visually and showed no sign of damage or detrimental effect from the test.

A four-unit system of this invention was installed on a commercial airlines jet aircraft. The system accumulated more than 2,500 hours of flying time under the normal vibration conditions encountered in jet aircraft, functioning perfectly as indicated by its own test and by several maintenance tests and inspections. Over the period of time no false alarm took place for whatever cause. No system of this invention has, in fact, yet caused a false alarm.

(5) Salt spray The FAA standards require: The instrument components which are to be installed in exposed portions of the aircraft shall be subjected to a finely atomized spray of 20 percent sodium chloride solution for 50 hours. At the end of this period, the component shall be allowed to dry and may then be cleaned prior to conducting the test per paragraph 7.1 (paragraph 7.1 is the response time test described above).

A unit of this invention was exposed to a finally atomized spnay of 20% sodium chloride for a continuous period of 200 hours. After the test the unit was washed and dried and inspected visually. It showed minor isolate-d pits, but otherwise was in perfect condition and it operated perfectly.

(6) Humidity The FAA standards say: The instrument shall be mounted in a chamber maintained at a temperature of 70+2 C. and a relative humidity of 95 +5 for a period of six hours. After this period, the heat shall be shut off and the instrument shall be allowed to cool for a period of 16 hours in this atmosphere in which the humidity rises to 100% as the temperature decreases to not more than 38 C. This complete cycle shall be conducted:

(21) Five times for components located in uncontrolled temperature areas.

(b) Once for components located in controlled temperature areas.

Immediately after this cycling, there shall be no evidence of damage or corrosion which affects performance."

A unit embodying this invention was exposed to saturated water vapor in air at a temperature of 211 F. for five periods of at least six hours each, the periods being separated by periods of from 12 to 20 hours during which the unit and its atmosphere were allowed to cool. At the end of this test the unit was inspected visually and showed no sign of damage or detrimental effect from the test.

(7) Immersion in fuel and in oil The unit used in the humidity test was immersed in normal internal combustion engine fuel and was allowed to drain for one minute. The unit was unaffected by this test. The same unit was immersed in engine lubricating oil and allowed to drain for one minute. The unit was also unaffected by this test. Both tests were FAA standard tests.

(8) Sand blasting In conformity to the FAA standards, a unit of this invention was exposed to a sand-laden air stream flowing at 2% pounds per hour for four hours. The sand was l50 mesh and finer. At the end of the test the unit showed no damage or detrimental effect from the test.

(9) High temperature operation and low temperature operation In further conformity to FAA standards, a unit of this invention which had previously undergone three one-minute exposures to a totally enveloping 2000 F. flame was operated in an air furnace at a temperature of 400 F. for 65 hours continuously. At the end of this period, while the rest of the unit remained in the furnace, a six-inch section of its sensor was exposed to a 2000 F. flame from a standard fire detector test burner. The unit signalled an alarm in 4.5 seconds and, after removal from the flame, the unit cleared the alarm in one second.

The same unit which had previously undergone three one-minute exposures to a totally enveloping 2000 F. flame was operated in a Dry Ice-acetone bath at a temperature of F. for 50 hours continuously. At the end of this period, while the rest of the unit remained in the bath, a six-inch section of its sensor was exposed to a 2000 F. flame from a standard fire detector test burner. The unit signalled an alarm in 5 seconds and, after removal from the flame, the unit cleared the alarm in 1 second.

(10) High altitude The FAA standards say in section 7.10.1, The instrument shall be subjected to a pressure that is varied from normal atmospheric pressure to an altitude pressure equivalent to 50,000 feet at a rate of not less than 3,000 feet per minute. The instrument shall be maintained at the altitude pressure equivalent to 50,000 feet for a period of 48 hours. The instrument shall then be returned to sea level conditions and then tested per paragraph 7.1.

A unit of this invention was placed in a vacuum chamher which was maintained at a pressure of about one micron of mercury for 66 hours continuously. At the end of this period the unit was removed from the chamber and a six-inch section of its sensor was exposed to a 2000 F. flame from a standard fire tes't burner. The unit signalled an alarm in 3.9 seconds and, after removal from the flame, the unit cleared the alarm in one second.

(11) Low altitude and pressurizdtion The FAA standards say in section 7.10.2 and 7.10.3. Low altitude: The instrument shall be subjected to the same test as outlined in paragraph 7.10.1, except that the pressure shall be maintained at an altitude pressure equivalent to 1000 feet and that the rate of pressure variation need not be as specified therein.

Pressurization test: The components which are to be located in a pressurized area shall be subjected to an external pressure of 50 inches of mercury absolute for a period of 15 minutes. The response time test of the instrument per paragraph 7.1 shall be conducted while the component involved is under this pressure. 

